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2021-04-14: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and A350-1041 airplanes. This AD was prompted by reports that suitable corrosion protection treatment had not been applied to certain areas of the seat track. This AD requires a one-time detailed inspection of the seat tracks between certain frames for suitable corrosion protection or presence of corrosion, and on- condition actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
75-17-03: 75-17-03 HANDLEY PAGE (SCOTTISH AVIATION, LTD.): Amendment 39-2305. Applies to Jetstream Model HP-137 Mark I airplanes that do not have Handley Page Modification No. 1219 incorporated. Compliance is required as indicated. To provide for adequate depth of engagement of wing-fuselage fittings accomplish the following: (a) For Jetstream airplanes Serial Numbers 213, 216, 217, 218, 220, 221, 224, 237, 238, and 246, within the next 100 hours' time in service after the effective date of this AD or, prior to the accumulation of a total of 2,500 landings, whichever occurs later, unless already accomplished, comply with paragraph (c) of this AD. (b) For all other airplanes, within the next 100 hours' time in service after the effective date of this AD, unless already accomplished, radiographically inspect spigots, P/N 13781B-5, for depth of engagement of the spigot in its housing in accordance with paragraph 2 (2) of Handley Page Jetstream Service Bulletin No. 7/1, IssueNo. 3, dated February 1970, or an FAA-approved equivalent. (1) If the spigot is found during the inspection required by this paragraph to be recessed in its housing by an amount more than 0.26 inches, before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where this work can be performed, comply with paragraph (c) of this AD. (2) If the spigot is found during the inspection required by this paragraph to be recessed in its housing by an amount of 0.26 inches or less, but greater than 0.20 inches, before the accumulation of a total of 2,500 landings, comply with paragraph (c) of this AD. (c) Replace affected spigots by accomplishing one of the following: (1) Install a longer spigot, P/N 13781B-7. (2) Install a new spigot of the same part number that is shown by radiographic inspection performed in accordance with paragraph 2 (2) of Handley Page Jetstream Service Bulletin No. 7/1, Issue No. 3, dated February 1970,or an FAA-approved equivalent to be recessed in its housing by an amount not exceeding 0.26 inches, and comply with paragraph (d) of this AD, as applicable. (d) For replacement spigots, P/N 13781B-5, that are found during an inspection required by paragraph (c) of this AD to be recessed by an amount of 0.26 inches or less but exceeding 0.20 inches, before the accumulation of 2,500 landings on the replacement spigot, comply with paragraph (c) of this AD. (e) For the purpose of complying with this AD, and subject to acceptance by the assigned FAA Maintenance Inspector, the number of landings may be established by dividing each airplane's hours' time in service by the operator's fleet average flight time from takeoff to landing for the Model HP137 Jetstream airplane. This amendment becomes effective September 1, 1975.
2014-05-09: We are superseding Airworthiness Directive (AD) 2012-12-08 for certain The Boeing Company Model 777-200 and -300 series airplanes. AD 2012-12-08 required an inspection for the part number of the main landing gear retract actuator fuse pin, and replacement of the pin if necessary. This new AD retains the actions required by AD 2012-12-08 and adds airplanes to the applicability. This AD was prompted by a determination that additional airplanes may be subject to the identified unsafe condition. We are issuing this AD to prevent structural damage to the side and drag brace lock assemblies, which could result in landing gear collapse during touchdown, rollout, or taxi.
99-21-05: This amendment supersedes Airworthiness Directive (AD) 77-25-03, which currently requires repetitively inspecting for cracks on the landing gear actuator rod ends that are equipped with grease fittings, on Fairchild Aircraft, Inc. (Fairchild Aircraft) Models SA226-T, SA226-AT, and SA226-TC airplanes. AD 77-25-03 also requires replacing the landing gear actuator rod ends with an improved part either immediately or at a certain time period depending on the results of the inspections. Replacement of all six rod ends terminates the repetitive inspection requirements of AD 77-25-03. This AD is the result of failures of the landing gear rod ends on airplanes where the rod ends were replaced in accordance with AD 77-25-03. Fairchild has re-designed the landing gear rod ends as a result of these failures. This AD requires replacing all landing gear rod ends with these improved design parts on all SA226 series airplanes, including those manufactured since AD 77-25-03 was issued (i.e., the Model SA226-T(B) airplanes). The actions specified by this AD are intended to prevent failure of the landing gear actuator caused by cracks in the rod ends, which could result in the inability to lower the landing gear during a landing with consequent possible loss of control of the airplane.
2014-05-01: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters. This AD requires analyzing the main gearbox (MGB) oil for indications of metal chips or pieces, reviewing the MGB log or equivalent record, and inspecting certain teeth in the MGB after two chip indications. This AD was prompted by a partial tooth rupture found in an MGB that was returned to the manufacturer for repairs. The actions of this AD are intended to detect wear in the MGB that could lead to a gear tooth rupture, failure of the MGB, loss of power to the main rotor, and subsequent loss of control of the helicopter.
76-23-02: 76-23-02 ROCKWELL: Amendment 39-2770. Applies to Model 114, S/N's 14089 through 14113, 14115 through 14122, 14125 through 14131, 14134 through 14149, 14152 through 14154, and 14156 through 14158. Compliance required as indicated after receipt of this AD. 1. Within 10 hours after the effective date of this AD, unless already accomplished, modify the forward cabin vent valve and air ducts in accordance with Rockwell Service Bulletin No. SB-114-6 dated November 1, 1976, or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. 2. Until compliance with paragraph 1 above is accomplished, the following operating procedure is required: While climbing, the two vent valves located near the floor, below and outboard of the front seat passenger's leg must be in the full open position (allowing hot or cold air to pass from the duct into the passenger compartment). Also the cabin heat and/or the cabin vent knobs located on the lower instrument panel just to the right of the center console must be in the full open position (pulled out to stop). Operation in taxi, cruise, or glide is exempt from these restrictions. This amendment is effective November 26, 1976, and was effective upon receipt for all recipients of the letter dated November 5, 1976, which contained this amendment.
99-21-06: This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-81, -82, -83, and -87 series airplanes (MD-81, -82, -83, and -87), and Model MD-88 airplanes, that currently requires visual or eddy current inspections to detect cracks of the actuator cylinder support brackets of the slat drive mechanism assembly, and replacement of any cracked brackets. This amendment continues to require repetitive eddy current inspection, adds an inspection requirement, and expands the area of inspection. This amendment also provides terminating action for the repetitive inspections. This amendment is prompted by reports indicating that additional cracking was found outside the original inspection area. The actions specified by this AD are intended to prevent inadvertent slat retraction in flight.
2014-03-06: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracks found in the aft support fitting, the rear spar upper chord, and the rear spar web. This AD requires repetitive inspections for cracking of the aft support fitting for the main landing gear (MLG) beam, and the rear spar upper chord and rear spar web in the area of rear spar station (RSS) 224.14; and repair if necessary. We are issuing this AD to detect and correct such cracks, which could grow and result in a fuel leak and possible fire.
99-21-07: This amendment supersedes two existing airworthiness directives (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (military) series airplanes, and Model MD-88 airplanes, that currently require installation of hydraulic line restrictors in the main landing gear (MLG), and modification or replacement of the left and right MLG hydraulic damper assemblies. This amendment requires an additional modification of the MLG hydraulic damper assemblies, or replacement of the MLG hydraulic damper assemblies with modified and reidentified hydraulic damper assemblies. This amendment is prompted by reports indicating that MLG hydraulic damper assemblies removed for overhaul had failed or damaged spring retainers, due to insufficient material thickness of the spring retainers. The actions specified by this AD are intended to prevent failure of the hydraulic damper assemblies of the MLG, which could result in vibration damage and collapse of the MLG.
99-21-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727-100 and -100C series airplanes, that requires replacement of certain skin panels of the lower fuselage with non-bonded skin panels. This amendment is prompted by reports of corrosion of the skin panels of the lower fuselage on airplanes with hot-bonded doublers. The actions specified by this AD are intended to prevent degradation of the structural integrity of certain skin panels of the lower fuselage, which could result in loss of airplane pressurization.
88-04-08: 88-04-08 SUD AVIATION: Amendment 39-5853. Applies to Model Caravelle SE210 series airplanes, as listed in Sud Service Bulletin Number 32-121, dated September 9, 1982, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent breakage of main landing gear manual uplock release mechanism screwjack shaft, accomplish the following: A. Prior to the accumulation of 2,500 landings or 12 months, whichever occurs first after the effective date of this AD, perform inspections of the square end fitting (LH and RH sides) P/N 210.43.20.123 and screwjack shafts P/N 210.43.20/122 or P/N 210.43.20.920, as described in paragraph 4B of Caravelle Sud Service Bulletin No. 32-121, dated September 8, 1982. B. Repeat the inspection required by paragraph A., above, as follows: 1. At intervals not exceeding 5,000 landings or 2 years, whichever occurs first, for aircraft on which the procedures described in Sud Service Bulletin 32-96 havenot been accomplished. 2. At intervals not exceeding 15,000 landings or 6 years, whichever occurs first, for aircraft on which the procedures described in Sud Service Bulletin 32-96 have been accomplished. C. In the event that damage or cracks are detected on the square end fitting or screwjack shaft, or there are more than two pin holes on the screwjack shaft, replace affected parts in accordance with Sud Service Bulletin No. 32-96, Revision 3, dated January 18, 1982. D. An alternate means of compliance or adjustment of the compliance times, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by thisdirective who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Sud Aviation/Aerospatiale, 316 Route de Bayonne, 31060 Toulouse Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective April 5, 1988.
2014-04-12: We are adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model EC225LP helicopters. This AD adds a new operating limitation that requires increasing the minimum density altitude flight limitation for helicopters without certain Eurocopter modifications installed. This AD is prompted by a report that flights below a certain density altitude create oscillations in the main rotor which can transfer dynamic loads to the structure, the main gearbox (MGB), and the main servo-control inputs, which could result in subsequent loss of control of the helicopter.
99-21-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 series airplanes, that currently requires a one-time inspection to detect chafing of electrical wires in the cable trough below the cabin floor; repair, if necessary; installation of additional tie-mounts and tie-wraps; and application of sealant to rivet heads. This amendment requires the accomplishment of these same actions on additional airplanes. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent chafing of electrical wires, which could result in an uncommanded shutdown of an engine during flight.
99-21-13: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model AS332C, L, and L1 helicopters, that requires inspecting and replacing certain bolts that secure the hoist arm lower fitting. This amendment is prompted by a report of a failure of the bolts that secure the hoist arm lower fitting during a factory load test. The actions specified by this AD are intended to prevent failure of the bolts that secure the hoist arm lower fitting, separation of components from the helicopter, impact with the main or tail rotor, and subsequent loss of control of the helicopter.
90-08-05: 90-08-05 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 6561. Docket No. 89-NM-227-AD. Applicability: De Havilland Model DHC-8 series airplanes, Serial Numbers 1 through 179, certificated in any category. Compliance: Required within 12 months after the effective date of this AD, unless previously accomplished. To ensure the proper operation of the emergency lighting system when required, accomplish the following: A. Relocate the emergency lights circuit breaker on the circuit breaker panel from the right essential bus to the right secondary bus and terminate a wire, in accordance with the Accomplishment Instructions of de Havilland Service Bulletin No. 8-33-17, dated August 25, 1989. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, New York Aircraft Certification Office, ANE-170, FAA, New England Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, New York Aircraft Certification Office, ANE-170. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing of Canada, Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment (39-6561, AD 90-08-05) becomes effective on May 4, 1990.
87-07-07: 87-07-07 BRITISH AEROSPACE: Amendment 39-5589. Applies to all Model BAC 1- 11 200 and 400 series airplanes, certificated in any category. Compliance is required prior to the accumulation of 12,000 landings, or within the next 1,500 landings after the effective date of this AD, whichever occurs later. To prevent failure of the keel structure to carry design loads due to structural crack propagation in the keel beam lateral diaphragm, accomplish the following, unless previously accomplished: A. Inspect, and repair or replace, as necessary, the keel beam lateral diaphragm assembly in accordance with BAC 1-11 Alert Service Bulletin 53-A-PM5918, dated May 6, 1986. B. Repeat the requirements of paragraph A., above, at intervals not to exceed 3,600 landings. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the manager, Standardization Branch, ANM-113, FAA, NorthwestMountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the requirements of this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to British Aerospace, Inc., Librarian, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective May 1, 1987.
2014-04-08: We are adopting a new airworthiness directive (AD) for all Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports of burr marks on the primary wheels, and cracked rings on the primary wheel shaft, on certain horizontal stabilizer trim actuators (HSTAs). This AD requires replacing certain HSTAs. We are issuing this AD to prevent burr marks on the primary wheels, and cracked rings on the primary wheel shaft, on certain HSTAs, which may lead to a disconnect of the pitch trim surface and subsequent loss of pitch control, resulting in loss of control of the airplane.
2014-04-04: We are adopting a new airworthiness directive (AD) for certain Diamond Aircraft Industries GmbH Models DA 42 NG and DA 42 M-NG airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as the failure of the alternator indication system to indicate warning when one alternator is inoperative. We are issuing this AD to require actions to address the unsafe condition on these products.
2010-16-03: We are adopting a new airworthiness directive (AD) for certain Model MD-11 and MD-11F airplanes. This AD requires revising the airplane flight manual to advise the flightcrew to use certain procedures during descent in certain icing conditions. This AD results from reports of several in-flight engine flameouts, including multiple dual engine flameout events, in ice-crystal icing conditions. We are issuing this AD to ensure that the flightcrew has the proper procedures to follow in certain icing conditions. These certain icing conditions could cause a multiple engine flameout during flight with the potential inability to restart the engines, and consequent forced landing of the airplane.
99-19-23: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-19-23 which was sent previously to all known U.S. owners and operators of Eurocopter France Model EC 120B helicopters by individual letters. This AD requires, at specified time intervals, inspecting the engine coupling tube for cracks and replacing any cracked engine coupling tube with an airworthy engine coupling tube. This amendment is prompted by the discovery, during routine maintenance inspections, of three cracked engine coupling tubes caused by structural resonance. The actions specified by this AD are intended to detect a crack in the engine coupling tube which could result in coupling failure, loss of engine drive, and a subsequent forced landing.
99-21-02: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-30, SD3-60, SD3-SHERPA, and SD3-60 SHERPA series airplanes, that requires detailed visual and borescopic inspections to detect corrosion of the engine mounting tube assembly, and replacement of corroded parts with new or serviceable parts. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the engine mounting tube assembly, which could result in loss of the engine in flight.
2022-16-04: The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Aerospace Corporation (Gulfstream) Model GV and GV-SP airplanes. This AD was prompted by corrosion of the horizontal stabilizer lower bonded skin assemblies. This AD requires inspecting the horizontal stabilizer lower skin and associated bonded doublers and bonded stringers, repairing any area with corrosion beyond allowable damage limits, and incorporating revisions to the airworthiness limitations section (ALS) in the existing aircraft maintenance manual (AMM) or progressive maintenance program. The FAA is issuing this AD to address the unsafe condition on these products.
93-16-07: 93-16-07 BRITISH AEROSPACE: Amendment 39-8664. Docket 93-NM-31-AD. Applicability: Model BAe 146 series airplanes; on which Fairey Hydraulics airbrake servo-valve assembly, part number 3799H1, has been installed; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent malfunction of the airbrake; this could result in uncommanded airbrake extension or retraction, which, subsequently, could adversely affect airplane performance, accomplish the following: (a) Within 90 days after the effective date of this AD, perform a visual inspection to determine whether Abex servo-valve, part number 72189, has been installed and to identify the serial number on the Abex servo-valve, in accordance with British Aerospace BAe 146 Inspection Service Bulletin S.B. 27-133, dated January 31, 1992. (1) If an Abex servo-valve, part number 72189, has been installed, having a serial number listed in Table I of the service bulletin: Prior to further flight, accomplish the requirements of paragraphs (a)(1)(i) and (a)(1)(ii) of this AD. (i) Remove the existing servo-valve assembly in accordance with the service bulletin. (ii) Perform a visual inspection to detect metallic debris in the filter mesh in the servo-valve in accordance with the service bulletin. If any debris is detected, replace the currently installed airbrake actuator with a new or serviceable airbrake actuator, and install a new or serviceable servo-valve assembly in accordance with the service bulletin. (2) If an Abex servo-valve has been installed and has a serial number listed in Table 2 of the service bulletin: Prior to further flight, reidentify the servo-valve in accordance with the service bulletin. (3) If an Abex servo-valve has been installed and has a serial number not listed in either Table 1 or 2 of the service bulletin: No further action is required by this AD. (b) As of the effective date of this AD, no FaireyHydraulics airbrake servo-valve assembly, part number 3799H1, shall be installed on any airplane unless that airbrake servo-valve assembly is in compliance with the requirements of this AD. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The inspection, removal, replacement, and reidentification shall be done in accordance with British Aerospace BAe 146 Inspection Service Bulletin S.B. 27-133, dated January 31, 1992, which includes Appendix A1 to Service Bulletin S.B. 27-133, dated January 31, 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from British Aerospace, Inc., Avro Division, 22070 Broderick Drive, Sterling, Virginia 20166. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on October 4, 1993.
93-14-20: 93-14-20 PRATT & WHITNEY: Amendment 39-8645. Docket No. 91-ANE-05. Applicability: Pratt & Whitney (PW) JT9D-59A, -70A, -7Q, and -7Q3 turbofan engines installed on, but not limited to Boeing 747, McDonnell Douglas DC-10, and Airbus A300 aircraft, in which the following high pressure turbine (HPT) stage 2 vane assemblies, identified by vane cluster assembly part numbers, are installed: 743772, 774872, 806272, 807372, 807772, 807072, and 808372. Compliance: Required as indicated, unless previously accomplished. To prevent uncontained HPT stage 2 blade fractures or lenticular airseal failures, accomplish the following: (a) For engines that have not incorporated the requirements of PW Service Bulletin (SB) 5566, Revision 5, dated August 10, 1990, and the requirements of PW SB 5428, Revision 3, dated March 12, 1984, borescope inspect the HPT stage 2 vanes in accordance with the Accomplishment Instructions of PW SB 5667, Revision 2, dated June 11, 1992, and in accordance withthe criteria identified in the applicable PW Maintenance Manual (MM) listed in paragraph (c) of this AD, prior to accumulating 1,000 hours time in service (TIS) since vane installation, or within the next 125 hours TIS after the effective date of this AD, whichever occurs later, and remove from service, prior to further flight, second stage turbine vanes exhibiting distress beyond serviceable limits. (b) For engines that have incorporated the requirements of PW SB 5566, Revision 5, dated August 10, 1990, and PW SB 5428, Revision 3, dated March 12, 1984, borescope inspect the HPT stage 2 vanes in accordance with the Accomplishment Instructions of PW SB 5667, Revision 2, dated June 11, 1992, and in accordance with the criteria identified in the applicable PW MM listed in paragraph (c) of this AD, prior to accumulating 2,000 hours total part TIS since new on the entire set of vanes, or within 1,000 hours TIS since vane installation, or within the next 125 hours TIS after the effectivedate of this AD, whichever occurs later, and remove from service, prior to further flight, second stage turbine vanes exhibiting distress beyond serviceable limits. (c) Thereafter, inspect the HPT stage 2 vanes in accordance with the criteria identified in the following PW MMs, and remove from service, prior to further flight, HPT stage 2 vanes exhibiting distress beyond serviceable limits. Engine Models MM Part Number/ Revision Date Section/Table JT9D-7Q/7Q3 783777/December 25, 1989 72-00-00/604A JT9D-59A/-70A 783778/April 25, 1990 72-00-00/605A JT9D-59A 783779/September 15, 1989 72-00-00/605 (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from Engine Certification Office. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The inspections shall be done in accordance with the following service document: Document No. Pages Issue Date PW SB No. 5667 1-6 Revision 2 June 11, 1992 Total pages: 6 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Pratt & Whitney, Publications Department, 400 Main Street, East Hartford, CT 06108. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on August 27, 1993.
98-17-01 R1: This amendment revises an existing airworthiness directive (AD), applicable to AlliedSignal Inc. TFE731 series turbofan engines, that currently requires installation of an improved flexible (flex) fuel tube. This amendment clarifies that installation of the improved flex fuel tube and that the use of a clamp on the original rigid fuel tube are optional for engines installed on Learjet 35, 36, and 55 series airplanes. This amendment is prompted by confusion from operators regarding the applicability of these Learjet engine installations. The actions specified by this AD are intended to prevent cracking of the fuel tube and the subsequent leakage of fuel on or around electrical components, which can cause an engine fire.